kpayne on VMOFRWIN702 with $$_JOB

Federal Aviation Administration, DOT

Pt. 60, App. C

control the helicopter dynamics, particularly in the presence of external disturbances. The motion system should meet basic
objective performance criteria, and be subjectively tuned at the pilot-s seat position to
represent the linear and angular accelerations of the helicopter during a prescribed
minimum set of maneuvers and conditions.
The response of the motion cueing system
should be repeatable.
(2) The Motion System tests in Section 3 of
Table C2A are intended to qualify the FFS
motion cueing system from a mechanical
performance standpoint. Additionally, the
list of motion effects provides a representative sample of dynamic conditions that
should be present in the flight simulator. An
additional list of representative, trainingcritical maneuvers, selected from Section 1,
(Performance tests) and Section 2, (Handling
Qualities tests) in Table C2A, that should be
recorded during initial qualification (but
without tolerance) to indicate the flight simulator motion cueing performance signature
have been identified (reference Section 3.e).
These tests are intended to help improve the
overall standard of FFS motion cueing.
b. Motion System Checks. The intent of
test 3a, Frequency Response, test 3b, Leg
Balance, and test 3c, Turn-Around Check, as
described in the Table of Objective Tests, is
to demonstrate the performance of the motion system hardware, and to check the integrity of the motion set-up with regard to
calibration and wear. These tests are independent of the motion cueing software and
should be considered robotic tests.
c. Motion System Repeatability. The intent of this test is to ensure that the motion
system software and motion system hardware have not degraded or changed over
time. This diagnostic test should be completed
during
continuing
qualification
checks in lieu of the robotic tests. This will
allow an improved ability to determine
changes in the software or determine degradation in the hardware. The following information delineates the methodology that
should be used for this test.
(1) Input: The inputs should be such that
rotational accelerations, rotational rates,
and linear accelerations are inserted before
the transfer from helicopter center of gravity to pilot reference point with a minimum
amplitude of 5 deg/sec/sec, 10 deg/sec and 0.3
g, respectively, to provide adequate analysis
of the output.
(2) Recommended output:
(a) Actual platform linear accelerations;
the output will comprise accelerations due
to both the linear and rotational motion acceleration;
(b) Motion actuators position.
d. Motion Cueing Performance Signature.
(1) Background. The intent of this test is
to provide quantitative time history records
of motion system response to a selected set

of automated QTG maneuvers during initial
qualification. It is not intended to be a comparison of the motion platform accelerations
against the flight test recorded accelerations
(i.e., not to be compared against helicopter
cueing). If there is a modification to the initially qualified motion software or motion
hardware (e.g., motion washout filter, simulator payload change greater than 10%) then
a new baseline may need to be established.
(2) Test Selection. The conditions identified in Section 3.e. in Table C2A are those
maneuvers where motion cueing is the most
discernible. They are general tests applicable
to all types of helicopters and should be completed for motion cueing performance signature at any time acceptable to the NSPM
prior to or during the initial qualification
evaluation, and the results included in the
MQTG.
(3) Priority. Motion system should be designed with the intent of placing greater importance on those maneuvers that directly
influence pilot perception and control of the
helicopter motions. For the maneuvers identified in section 3.e. in Table C2A, the flight
simulator motion cueing system should have
a high tilt co-ordination gain, high rotational gain, and high correlation with respect to the helicopter simulation model.
(4) Data Recording. The minimum list of
parameters provided should allow for the determination of the flight simulator-s motion
cueing performance signature for the initial
qualification evaluation. The following parameters are recommended as being acceptable to perform such a function:
(a) Flight model acceleration and rotational rate commands at the pilot reference
point;
(b) Motion actuators position;
(c) Actual platform position;
(d) Actual platform acceleration at pilot
reference point.
e. Motion Vibrations.
(1) Presentation of results. The characteristic motion vibrations may be used to
verify that the flight simulator can reproduce the frequency content of the helicopter
when flown in specific conditions. The test
results should be presented as a Power Spectral Density (PSD) plot with frequencies on
the horizontal axis and amplitude on the
vertical axis. The helicopter data and flight
simulator data should be presented in the
same format with the same scaling. The algorithms used for generating the flight simulator data should be the same as those used
for the helicopter data. If they are not the
same then the algorithms used for the flight
simulator data should be proven to be sufficiently comparable. As a minimum the results along the dominant axes should be presented and a rationale for not presenting the
other axes should be provided.
(2) Interpretation of results. The overall
trend of the PSD plot should be considered

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